Controllability of Spacecraft Attitude Using Control Moment Gyroscopes
This technical note describes an application of nonlinear controllability theory to the problem of spacecraft attitude control using control moment gyroscopes (CMGs). Nonlinear controllability theory is used to show that a spacecraft carrying one or more CMGs is controllable on every angular momentu...
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| Veröffentlicht in: | IEEE transactions on automatic control 2009-03, Vol.54 (3), p.585-590 |
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| creator | Bhat, S.P. Tiwari, P.K. |
| description | This technical note describes an application of nonlinear controllability theory to the problem of spacecraft attitude control using control moment gyroscopes (CMGs). Nonlinear controllability theory is used to show that a spacecraft carrying one or more CMGs is controllable on every angular momentum level set in spite of the presence of singular CMG configurations, that is, given any two states having the same angular momentum, any one of them can be reached from the other using suitably chosen motions of the CMG gimbals. This result is used to obtain sufficient conditions on the momentum volume of the CMG array that guarantee the existence of gimbal motions which steer the spacecraft to a desired spin state or rest attitude. |
| doi_str_mv | 10.1109/TAC.2008.2008324 |
| format | Article |
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Nonlinear controllability theory is used to show that a spacecraft carrying one or more CMGs is controllable on every angular momentum level set in spite of the presence of singular CMG configurations, that is, given any two states having the same angular momentum, any one of them can be reached from the other using suitably chosen motions of the CMG gimbals. This result is used to obtain sufficient conditions on the momentum volume of the CMG array that guarantee the existence of gimbal motions which steer the spacecraft to a desired spin state or rest attitude.</description><identifier>ISSN: 0018-9286</identifier><identifier>EISSN: 1558-2523</identifier><identifier>DOI: 10.1109/TAC.2008.2008324</identifier><identifier>CODEN: IETAA9</identifier><language>eng</language><publisher>New York, NY: IEEE</publisher><subject>Angular momentum ; Applied sciences ; Arrays ; Attitude control ; Computer science; control theory; systems ; Control moment gyroscopes ; Control system analysis ; Control theory. 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Nonlinear controllability theory is used to show that a spacecraft carrying one or more CMGs is controllable on every angular momentum level set in spite of the presence of singular CMG configurations, that is, given any two states having the same angular momentum, any one of them can be reached from the other using suitably chosen motions of the CMG gimbals. This result is used to obtain sufficient conditions on the momentum volume of the CMG array that guarantee the existence of gimbal motions which steer the spacecraft to a desired spin state or rest attitude.</description><subject>Angular momentum</subject><subject>Applied sciences</subject><subject>Arrays</subject><subject>Attitude control</subject><subject>Computer science; control theory; systems</subject><subject>Control moment gyroscopes</subject><subject>Control system analysis</subject><subject>Control theory. Systems</subject><subject>Controllability</subject><subject>Exact sciences and technology</subject><subject>Fundamental areas of phenomenology (including applications)</subject><subject>Gimbals</subject><subject>Gyroscopes</subject><subject>Level set</subject><subject>Motion control</subject><subject>Nonlinearity</subject><subject>Physics</subject><subject>Rest</subject><subject>Solid dynamics (ballistics, collision, multibody system, stabilization...)</subject><subject>Solid mechanics</subject><subject>Space technology</subject><subject>Space vehicles</subject><subject>Spacecraft</subject><subject>Spinning</subject><subject>Torque</subject><subject>Wheels</subject><issn>0018-9286</issn><issn>1558-2523</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2009</creationdate><recordtype>article</recordtype><sourceid>RIE</sourceid><recordid>eNqF0b9vGyEUB3AUNVJcp3ukLqdKbSen73HAwWhZtVMpVYYkM8L8iM46Hy7gwf99cG1l6NAsIMTnPT34EnKDcIsI6sfTfHFLAeTfpaXsgkyQczmjnLYfyAQA5UxRKa7Ix5w39SgYwwlZLuJYUhwGs-6HvhyaGJrHnbHeJhNKMy-lL3vnm-fcjy_NGTe_49aPpVkdUsw27ny-JpfBDNl_Ou9T8rz8-bS4m90_rH4t5vczyySWujJGhbEOuPNgER264DrjqLBBBbN2obWOUeDIuHGWAauCrzuoAKxop-T7qe8uxT97n4ve9tn6Ov7o4z5rBa2gDLl8V8qOV8tlV-W3_8qWMVBKHOGXf-Am7tNY36ulQKqYpMcJ4YRs_ZucfNC71G9NOmgEfUxK16T0MSR9TqqWfD33NdmaISQz2j6_1VFkHUVU1X0-ud57_3bNOiVahPYV6iKbWw</recordid><startdate>20090301</startdate><enddate>20090301</enddate><creator>Bhat, S.P.</creator><creator>Tiwari, P.K.</creator><general>IEEE</general><general>Institute of Electrical and Electronics Engineers</general><general>The Institute of Electrical and Electronics Engineers, Inc. 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Systems</topic><topic>Controllability</topic><topic>Exact sciences and technology</topic><topic>Fundamental areas of phenomenology (including applications)</topic><topic>Gimbals</topic><topic>Gyroscopes</topic><topic>Level set</topic><topic>Motion control</topic><topic>Nonlinearity</topic><topic>Physics</topic><topic>Rest</topic><topic>Solid dynamics (ballistics, collision, multibody system, stabilization...)</topic><topic>Solid mechanics</topic><topic>Space technology</topic><topic>Space vehicles</topic><topic>Spacecraft</topic><topic>Spinning</topic><topic>Torque</topic><topic>Wheels</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Bhat, S.P.</creatorcontrib><creatorcontrib>Tiwari, P.K.</creatorcontrib><collection>IEEE All-Society Periodicals Package (ASPP) 2005-present</collection><collection>IEEE All-Society Periodicals Package (ASPP) 1998-Present</collection><collection>IEEE Electronic Library (IEL)</collection><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>Computer and Information Systems Abstracts</collection><collection>Electronics & Communications Abstracts</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>ProQuest Computer Science Collection</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Computer and Information Systems Abstracts Academic</collection><collection>Computer and Information Systems Abstracts Professional</collection><collection>ANTE: Abstracts in New Technology & Engineering</collection><collection>Aerospace Database</collection><jtitle>IEEE transactions on automatic control</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Bhat, S.P.</au><au>Tiwari, P.K.</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Controllability of Spacecraft Attitude Using Control Moment Gyroscopes</atitle><jtitle>IEEE transactions on automatic control</jtitle><stitle>TAC</stitle><date>2009-03-01</date><risdate>2009</risdate><volume>54</volume><issue>3</issue><spage>585</spage><epage>590</epage><pages>585-590</pages><issn>0018-9286</issn><eissn>1558-2523</eissn><coden>IETAA9</coden><abstract>This technical note describes an application of nonlinear controllability theory to the problem of spacecraft attitude control using control moment gyroscopes (CMGs). 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| identifier | ISSN: 0018-9286 |
| ispartof | IEEE transactions on automatic control, 2009-03, Vol.54 (3), p.585-590 |
| issn | 0018-9286 1558-2523 |
| language | eng |
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| source | IEEE Electronic Library (IEL) |
| subjects | Angular momentum Applied sciences Arrays Attitude control Computer science control theory systems Control moment gyroscopes Control system analysis Control theory. Systems Controllability Exact sciences and technology Fundamental areas of phenomenology (including applications) Gimbals Gyroscopes Level set Motion control Nonlinearity Physics Rest Solid dynamics (ballistics, collision, multibody system, stabilization...) Solid mechanics Space technology Space vehicles Spacecraft Spinning Torque Wheels |
| title | Controllability of Spacecraft Attitude Using Control Moment Gyroscopes |
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